FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.64 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w097-il-1000000.txt Download as CSV file: xf-fx84w097-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-097
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4001 0.12920 0.12775 -0.0018 1.0000 0.0118
-12.000 -0.4027 0.12380 0.12236 -0.0036 1.0000 0.0122
-9.750 -0.7335 0.03041 0.02801 -0.0555 0.9829 0.0090
-9.500 -0.7145 0.02766 0.02496 -0.0568 0.9536 0.0092
-9.250 -0.7037 0.02549 0.02248 -0.0554 0.9308 0.0094
-9.000 -0.6871 0.02406 0.02083 -0.0544 0.9155 0.0096
-8.750 -0.6703 0.02215 0.01863 -0.0535 0.9026 0.0097
-8.500 -0.6512 0.02047 0.01667 -0.0528 0.8915 0.0099
-8.250 -0.6302 0.01905 0.01501 -0.0522 0.8816 0.0102
-8.000 -0.6082 0.01775 0.01346 -0.0516 0.8722 0.0104
-7.750 -0.5847 0.01662 0.01214 -0.0512 0.8632 0.0108
-7.500 -0.5605 0.01567 0.01098 -0.0507 0.8550 0.0111
-7.250 -0.5350 0.01501 0.01017 -0.0505 0.8466 0.0115
-7.000 -0.5083 0.01477 0.00983 -0.0503 0.8389 0.0118
-6.750 -0.4860 0.01289 0.00768 -0.0497 0.8308 0.0128
-6.500 -0.4596 0.01240 0.00712 -0.0495 0.8235 0.0134
-6.250 -0.4329 0.01200 0.00663 -0.0494 0.8157 0.0140
-6.000 -0.4059 0.01159 0.00615 -0.0492 0.8082 0.0148
-5.750 -0.3789 0.01122 0.00568 -0.0491 0.8006 0.0155
-5.500 -0.3512 0.01099 0.00539 -0.0490 0.7933 0.0161
-5.250 -0.3257 0.01012 0.00438 -0.0487 0.7860 0.0178
-5.000 -0.2981 0.00985 0.00408 -0.0486 0.7790 0.0190
-4.750 -0.2704 0.00966 0.00384 -0.0486 0.7717 0.0205
-4.500 -0.2424 0.00951 0.00365 -0.0486 0.7649 0.0216
-4.250 -0.2155 0.00898 0.00303 -0.0484 0.7578 0.0244
-4.000 -0.1876 0.00878 0.00280 -0.0484 0.7510 0.0268
-3.750 -0.1595 0.00866 0.00264 -0.0484 0.7438 0.0288
-3.500 -0.1319 0.00832 0.00228 -0.0483 0.7371 0.0339
-3.250 -0.1038 0.00818 0.00210 -0.0483 0.7297 0.0377
-3.000 -0.0759 0.00796 0.00187 -0.0483 0.7228 0.0460
-2.750 -0.0478 0.00779 0.00171 -0.0484 0.7154 0.0564
-2.500 -0.0198 0.00762 0.00157 -0.0484 0.7084 0.0708
-2.250 0.0083 0.00746 0.00145 -0.0485 0.7009 0.0906
-2.000 0.0363 0.00729 0.00134 -0.0485 0.6941 0.1186
-1.750 0.0643 0.00710 0.00125 -0.0486 0.6867 0.1537
-1.500 0.0921 0.00689 0.00117 -0.0487 0.6801 0.2044
-1.250 0.1199 0.00663 0.00110 -0.0488 0.6729 0.2691
-1.000 0.1472 0.00627 0.00104 -0.0489 0.6661 0.3746
-0.750 0.1740 0.00580 0.00099 -0.0490 0.6589 0.5168
-0.500 0.1998 0.00533 0.00098 -0.0487 0.6522 0.6777
-0.250 0.2257 0.00505 0.00101 -0.0482 0.6450 0.7800
0.000 0.2519 0.00496 0.00104 -0.0477 0.6380 0.8348
0.250 0.2779 0.00490 0.00106 -0.0471 0.6303 0.8747
0.500 0.3035 0.00489 0.00109 -0.0463 0.6229 0.9053
0.750 0.3288 0.00488 0.00111 -0.0455 0.6150 0.9310
1.000 0.3548 0.00490 0.00112 -0.0449 0.6076 0.9515
1.250 0.3837 0.00492 0.00113 -0.0450 0.5998 0.9688
1.500 0.4180 0.00497 0.00114 -0.0463 0.5922 0.9832
1.750 0.4562 0.00501 0.00115 -0.0485 0.5837 0.9914
2.000 0.4977 0.00506 0.00116 -0.0515 0.5741 0.9987
2.250 0.5264 0.00513 0.00119 -0.0518 0.5646 1.0000
2.500 0.5518 0.00521 0.00123 -0.0513 0.5553 1.0000
2.750 0.5778 0.00528 0.00129 -0.0510 0.5470 1.0000
3.000 0.6041 0.00539 0.00135 -0.0507 0.5376 1.0000
3.250 0.6310 0.00547 0.00141 -0.0505 0.5275 1.0000
3.500 0.6581 0.00556 0.00149 -0.0504 0.5178 1.0000
3.750 0.6852 0.00568 0.00158 -0.0503 0.5070 1.0000
4.000 0.7122 0.00582 0.00166 -0.0502 0.4877 1.0000
4.250 0.7389 0.00601 0.00177 -0.0501 0.4634 1.0000
4.500 0.7657 0.00621 0.00190 -0.0500 0.4413 1.0000
4.750 0.7925 0.00641 0.00204 -0.0499 0.4221 1.0000
5.000 0.8191 0.00666 0.00220 -0.0498 0.3962 1.0000
5.250 0.8450 0.00698 0.00239 -0.0496 0.3639 1.0000
5.500 0.8703 0.00739 0.00264 -0.0494 0.3241 1.0000
5.750 0.8943 0.00796 0.00297 -0.0491 0.2700 1.0000
6.000 0.9171 0.00868 0.00339 -0.0486 0.2094 1.0000
6.250 0.9390 0.00948 0.00387 -0.0481 0.1476 1.0000
6.500 0.9604 0.01033 0.00442 -0.0474 0.0917 1.0000
6.750 0.9832 0.01097 0.00489 -0.0469 0.0606 1.0000
7.000 1.0066 0.01151 0.00533 -0.0465 0.0425 1.0000
7.250 1.0302 0.01201 0.00577 -0.0460 0.0313 1.0000
7.500 1.0541 0.01245 0.00620 -0.0456 0.0254 1.0000
7.750 1.0778 0.01291 0.00667 -0.0451 0.0211 1.0000
8.000 1.0999 0.01350 0.00726 -0.0444 0.0173 1.0000
8.250 1.1232 0.01394 0.00773 -0.0439 0.0158 1.0000
8.500 1.1461 0.01440 0.00821 -0.0433 0.0143 1.0000
8.750 1.1671 0.01502 0.00887 -0.0425 0.0130 1.0000
9.000 1.1846 0.01592 0.00987 -0.0412 0.0120 1.0000
9.250 1.2061 0.01640 0.01039 -0.0404 0.0115 1.0000
9.500 1.2258 0.01698 0.01103 -0.0394 0.0110 1.0000
9.750 1.2454 0.01753 0.01162 -0.0385 0.0104 1.0000
10.000 1.2630 0.01819 0.01231 -0.0373 0.0100 1.0000
10.250 1.2786 0.01892 0.01310 -0.0358 0.0095 1.0000
10.500 1.2863 0.01995 0.01420 -0.0331 0.0091 1.0000
10.750 1.2809 0.02160 0.01600 -0.0289 0.0086 1.0000
11.000 1.2899 0.02257 0.01704 -0.0269 0.0085 1.0000
11.250 1.3026 0.02335 0.01788 -0.0254 0.0082 1.0000
11.500 1.3090 0.02466 0.01927 -0.0235 0.0081 1.0000
11.750 1.3189 0.02575 0.02044 -0.0221 0.0079 1.0000
12.000 1.3271 0.02706 0.02183 -0.0207 0.0076 1.0000
12.250 1.3328 0.02863 0.02349 -0.0193 0.0075 1.0000
12.500 1.3416 0.02999 0.02493 -0.0183 0.0073 1.0000
12.750 1.3483 0.03158 0.02660 -0.0173 0.0071 1.0000
13.000 1.3555 0.03318 0.02827 -0.0165 0.0069 1.0000
13.250 1.3613 0.03497 0.03012 -0.0158 0.0067 1.0000
13.500 1.3651 0.03702 0.03225 -0.0152 0.0065 1.0000
13.750 1.3649 0.03956 0.03489 -0.0146 0.0063 1.0000
14.000 1.3597 0.04278 0.03824 -0.0141 0.0061 1.0000
14.250 1.3483 0.04687 0.04251 -0.0136 0.0060 1.0000
14.500 1.3439 0.05030 0.04609 -0.0137 0.0059 1.0000
14.750 1.3385 0.05394 0.04987 -0.0140 0.0059 1.0000
15.000 1.3410 0.05675 0.05279 -0.0147 0.0058 1.0000
15.250 1.3397 0.06019 0.05635 -0.0155 0.0057 1.0000
15.500 1.3338 0.06443 0.06073 -0.0167 0.0057 1.0000
15.750 1.3306 0.06843 0.06485 -0.0181 0.0056 1.0000
16.000 1.3261 0.07280 0.06935 -0.0198 0.0055 1.0000
16.250 1.3153 0.07834 0.07505 -0.0221 0.0055 1.0000
16.500 1.3057 0.08393 0.08079 -0.0246 0.0055 1.0000
16.750 1.2932 0.09032 0.08733 -0.0276 0.0054 1.0000
17.000 1.2801 0.09701 0.09417 -0.0311 0.0054 1.0000
17.250 1.2644 0.10458 0.10191 -0.0351 0.0053 1.0000
17.500 1.2495 0.11219 0.10965 -0.0393 0.0054 1.0000
17.750 1.2327 0.12057 0.11819 -0.0442 0.0053 1.0000
18.000 1.2123 0.13010 0.12787 -0.0499 0.0054 1.0000
18.250 1.1924 0.13999 0.13791 -0.0559 0.0054 1.0000
18.500 1.1693 0.15111 0.14918 -0.0628 0.0055 1.0000
18.750 1.1363 0.16578 0.16403 -0.0718 0.0056 1.0000
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Polar data table (+)
Polar graphs
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